A dovetail seal assembly for sealing a gap between a bucket dovetail and a rotor. The dovetail seal assembly may include a sealing slot positioned about the dovetail, a high-pressure supply hole in communication with the sealing slot, and a deformable seal positioned about the sealing slot and into the gap.
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16. A method of sealing a gap between a bucket dovetail and a rotor, comprising:
positioning a deformable seal within a sealing slot of the dovetail;
forcing high-pressure fluid through the dovetail;
providing an inward compressive force on the deformable seal that counteracts a centrifugal load force due to rotation; and
forcing the deformable seal towards the rotor and into the gap with the high-pressure fluid.
1. A dovetail seal assembly for sealing a gap between a bucket dovetail and a rotor, comprising:
a sealing slot positioned in a radial plane about the dovetail;
a deformable seal positioned in a radial plane about the sealing slot and into the gap; and
a high-pressure supply hole in communication with the sealing slot such that the high-pressure pressure supply hole supplies an inward compressive force on the deformable seal that counteracts a centrifugal load force due to rotation and forces the deformable seal towards the rotor and into the gap.
10. A dovetail seal assembly for sealing a gap between a bucket dovetail and a rotor, comprising:
a sealing slot positioned in a radial plane about the dovetail;
a supply chamber positioned in a radial plane about the sealing slot;
a supply hole in communication with the supply chamber and a high pressure side of the dovetail; and
a deformable seal positioned in a radial plane about the sealing slot and forced into the gap via an inward compressive force way of high-pressure air passing from the high-pressure side of the dovetail into the supply hole, wherein the compressive force counteracts a centrifugal load force due to rotation and forces the deformable seal towards the rotor and into the gap.
2. The dovetail seal assembly of
3. The dovetail seal assembly of
4. The dovetail seal assembly of
5. The dovetail seal assembly of
6. The dovetail seal assembly of
7. The dovetail seal assembly of
8. The dovetail seal assembly of
9. The dovetail seal assembly of
11. The dovetail seal assembly of
12. The dovetail seal assembly of
13. The dovetail seal assembly of
14. The dovetail seal assembly of
15. The dovetail seal assembly of
19. The method of
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The present application relates generally to any type of turbine and more particularly relates to systems and methods for sealing a gap formed between a turbine bucket dovetail and a turbine rotor via gas pressure and a deformable seal material.
Gas turbines generally include a turbine rotor (wheel) with a number of circumferentially spaced buckets (blades). The buckets generally may include an airfoil, a platform, a shank, a dovetail, and other elements. The dovetail of each bucket is positioned within the turbine rotor and secured therein. The airfoils project into the hot gas path so as to convert the kinetic energy of the gas into rotational mechanical energy. A number of cooling medium passages may extend radially through the bucket to direct an inward and/or an outward flow of the cooling medium therethrough.
Leaks may develop in the coolant supply circuit based upon a gap between the tabs of the dovetails and the surface of the rotor due to increases in thermal and/or centrifugal loads. Air losses from the bucket supply circuit into the wheel space may be significant with respect to blade cooling medium flow requirements. Moreover, the air may be extracted from later compressor stages such that the penalty on energy output and overall efficiency may be significant during engine operation.
Efforts have been made to limit this leak. For example, one method involves depositing aluminum on a dovetail tab so as to fill the gap at least partially. Specifically, a circular ring may be pressed against the forward side of the dovetail face. Although this design seals well and is durable, the design cannot be easily disassembled and replaced in the field. Rather, these rings may only be disassembled when the entire rotor is disassembled.
There is thus a desire for improved dovetail tab sealing systems and methods. Such systems and methods should adequately prevent leakage therethrough so as to increase overall system efficiency while being installable and/or repairable in the field.
The present application thus provides a dovetail seal assembly for sealing a gap between a bucket dovetail and a rotor. The dovetail seal assembly may include a sealing slot positioned about the dovetail, a high-pressure supply hole in communication with the sealing slot, and a deformable seal positioned about the sealing slot and into the gap.
The present application further provides a dovetail seal assembly for sealing a gap between a bucket dovetail and a rotor. The dovetail seal assembly may include a sealing slot positioned about the dovetail, a supply chamber positioned about the sealing slot, a supply hole in communication with the supply chamber and a high pressure side of the dovetail, and a deformable seal positioned about the sealing slot and forced into the gap via high pressure air passing from the high pressure side of the dovetail into the supply hole.
The present application further provides a method of sealing a gap between a bucket dovetail and a rotor. The method includes the steps of positioning a deformable seal within a sealing slot of the dovetail, forcing high-pressure fluid through the dovetail, and forcing the deformable seal against the rotor with the high-pressure fluid.
These and other features of the present application will become apparent to one of ordinary skill in the art upon review of the following detailed description when taken into conjunction with the several drawings and the appended claims.
Referring now to the drawings, in which like numerals refer to like elements throughout the several views,
As is known, the bucket 10 may include an airfoil 30, a platform 40, a shank 50, a dovetail 60, and other elements. It will be appreciated that the bucket 10 is one of a number of circumferentially spaced buckets 10 secured to and about the rotor 20 of the turbine. The bucket 10 of
As described above, the rotor 20 may have a number of slots 25 for receiving the dovetails 60 of the buckets 10. Likewise, the airfoils 30 of the buckets 10 project into the hot gas stream so as to enable the kinetic energy of the stream to be converted into mechanical energy through the rotation of the rotor 20. The dovetail 60 may include a first tang or tab 70 and a second tab 80 extending therefrom. Similar designs may be used herein. A gap 90 may be formed between the ends of the tabs 70, 80 of the dovetail 60 and the rotor 20. A high pressure cooling flow may escape via the gap 90 unless a sealing system of some type is employed.
The dovetail seal assembly 100 may include a high-pressure supply chamber 120 positioned about the first tab 70 directly above the sealing slot 110. The high-pressure supply chamber 120 also may extend about the perimeter of the first tab 70 and may have any desired size or shape. The high-pressure supply chamber 120 also may be formed by conventional machining or other types of manufacturing techniques. A deeper sealing slot 110 may be used in place of a specific high-pressure supply chamber 120.
The dovetail seal assembly 100 may include a high-pressure supply hole 130 in communication with the high-pressure supply chamber 120. The high-pressure supply hole 130 extends from the high-pressure supply chamber 120 to the exterior of the first tab 70 about a high-pressure side 140 thereof. The high-pressure supply hole 130 may have any desired geometry or size. The high-pressure supply hole 130 also may be formed by conventional machining or other types of manufacturing techniques.
The dovetail seal assembly 100 may include a deformable seal 150 positioned about the sealing slot 110. The deformable seal 150 may have a substantially square cross-section, a nearly circular cross-section, a “c”-shape, or any other desired design. Specifically, an axial or a radial c-seal may be used. The deformable seal 150 may be made out of a woven graphite, woven metal, woven intermetallic, woven ceramic, sintered metal/graphite, vapor deposited graphite on a metal backing, hybrids of metal/graphite/ceramics, and other types of deformable materials. The deformable seal 150 may fill the sealing slot 110 as well as the gap 90 between the bucket 10 and rotor 20. Any number of seals 150 and supply holes 130 may be used herein.
In use, high-pressure air or other fluids from the high-pressure side 140 of the first tab 70 of the dovetail 60 extends into the high-pressure supply hole 130 and the high-pressure supply chamber 120. The high-pressure air presses or exerts a force against the deformable seal 150. The deformable seal 150 thus is forced against the rotor 20 such that the gap 90 is filled and high-pressure air is not allowed to leak therethrough. Specifically, the compressive force or other force on the deformable seal 150 counteracts the centrifugal loading force present as the bucket 10 rotates. The deformable seal 150 seals the gap 90 in whole or in part. Other types of sealing forces may be used herein.
The deformable seal 150 also may be used with other sealing systems and methods. The dovetail seal assembly 100 also may be used with the second tab 80 and elsewhere.
It should be apparent that the foregoing relates only to certain embodiments of the present application and that numerous changes and modifications may be made herein by one of ordinary skill in the art without departing from the general spirit and scope of the invention as defined by the following claims and the equivalents thereof.
Arness, Brian P., Ward, John D.
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Executed on | Assignor | Assignee | Conveyance | Frame | Reel | Doc |
Jun 24 2008 | ARNESS, BRIAN P | General Electric Company | ASSIGNMENT OF ASSIGNORS INTEREST SEE DOCUMENT FOR DETAILS | 021202 | /0039 | |
Jun 26 2008 | WARD, JOHN D | General Electric Company | ASSIGNMENT OF ASSIGNORS INTEREST SEE DOCUMENT FOR DETAILS | 021202 | /0039 | |
Jul 08 2008 | General Electric Company | (assignment on the face of the patent) | / |
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